US6261063B1 - Seal structure between gas turbine discs - Google Patents

Seal structure between gas turbine discs Download PDF

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Publication number
US6261063B1
US6261063B1 US09/230,848 US23084899A US6261063B1 US 6261063 B1 US6261063 B1 US 6261063B1 US 23084899 A US23084899 A US 23084899A US 6261063 B1 US6261063 B1 US 6261063B1
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US
United States
Prior art keywords
disk
sealing member
sealing
gas turbine
inter
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US09/230,848
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English (en)
Inventor
Rintaro Chikami
Kaoru Sakata
Takeshi Nakamura
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from JP14647597A external-priority patent/JP3310906B2/ja
Priority claimed from JP16264797A external-priority patent/JP3342347B2/ja
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD reassignment MITSUBISHI HEAVY INDUSTRIES, LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CHIKAMI, RINTARO, NAKAMURA, TAKESHI, SAKATA, KAORU
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the present invention relates to a steam cooling type gas turbine which is adopted in a combined cycle power plant or the like, and more particularly to a sealing structure for sealing spaces between disks to prevent the leakage of cooling steam in the gas turbine.
  • a combined cycle power plant is an electric power generating system in which a gas turbine plant and a steam turbine plant are combined, wherein the gas turbine is adapted to operate in a high temperature range of thermal energy and the steam turbine is employed in a low temperature range to recover and use thermal energy efficiently.
  • This type of power generating system has been attracting attention in recent years.
  • FIG. 9 and FIG. 10 A conventional sealing structure known heretofore will be described with reference to FIG. 9 and FIG. 10 .
  • the structure shown in these figures was first adopted in a gas turbine in which compressed air is employed as the coolant, and subsequently has been adopted in some steam cooling type gas turbines.
  • a rotor of a turbine section includes a plurality (ordinarily around four sets) of disks 1 .
  • annular projections (also referred to as disk lands) 6 are formed on the surfaces of adjacent disks 1 so as to face each other around a rotatable shaft, as shown in FIG.
  • grooves 7 are formed in protruding end faces of the projections 6 , respectively, so as to extend in a circumferential direction, and a seal plate (also referred to as a baffle plate) 8 divided into two or four parts in the circumferential direction in which the grooves 7 are disposed is inserted into the grooves 7 .
  • the baffle plate 8 is pressed against outer side walls of the grooves 7 , respectively, by centrifugal force generated upon rotation of the turbine, whereby sealing is obtained.
  • the baffle plate since the baffle plate has a predetermined rigidity, a situation may arise where the baffle plate can not be pressed snugly and uniformly against the outer side walls of the grooves formed in the disks because of the difference in elongation, and as a result, minute gaps may be formed between the grooves and the baffle plates.
  • the coolant confined within the interior of the rotor may flow to the gas path of the turbine section or the high-temperature gas may flow into the inner space from the gas path 4 .
  • the coolant continues to leak through the minute gaps, self-induced vibration of the baffle plate occurs causing abrasion of the baffle plate and other problems.
  • the present invention intends to solve the problems mentioned above in conjunction with the prior art and provide a sealing structure for a gas turbine which is capable of enhancing the sealing performance between the interior of a rotor and a gas path of a turbine section, and which thus contributes greatly to the practical applicability of the steam-jet cooling system.
  • the present invention has been made to achieve the object mentioned above and provides an inter-disk sealing structure for a gas turbine in which a plurality of rotor disks are disposed in juxtaposition with one another in the axial direction, wherein a groove extending in a circumferential direction is formed in an end face of at least one of two disk lands which protrude in opposition to each other between adjacent rotor disks, and wherein an annular sealing member having an interior space is disposed in a sandwiched fashion, being brought into contact under pressure with an inner wall surface of the groove and an end face of the other disk land, or alternatively, with an inner wall surface of a groove formed in the other disk land.
  • the present invention provides an inter-disk sealing structure for a gas turbine, in which the annular sealing member formed of a tube which is hollow in cross section is constituted by interconnecting a plurality of segments in the direction of the annular elongation thereof.
  • the annular sealing member By virtue of the structure of the annular sealing member constituted by interconnecting a plurality of segments in the direction of annular elongation, or in other words, in the circumferential direction to perform the inter-disk sealing in the gas turbine, the annular sealing member can stretch following the stretch or elongation of the rotor disks, which is thermally induced or occurs under the influence of centrifugal force, without being accompanied by stress in the circumferential direction due to centrifugal force, and a gap is not created in the seal portion.
  • the sealing performance can be positively maintained regardless of the difference in elongation between the adjacent rotor disks.
  • a sealing member having a generally M-shape cross-section may be adopted, wherein the sealing member mentioned above may be disposed in grooves formed in the end faces of the disk lands in a circumferential direction so that the sealing member can be brought into contact with the wall surfaces of the grooves extending in the radial direction of the rotor disks.
  • the sealing surface pressure can be increased under the influence of centrifugal force, and thus, the sealing performance can be reliably maintained regardless of the elongation or stretch of the rotor disk by properly selecting the contact points between the sealing member and the wall surface of the groove.
  • the sealing performance of the gas turbine is improved.
  • FIG. 1 is an explanatory view schematically showing an inter-disk sealing structure for a gas turbine according to an embodiment of the present invention.
  • FIG. 2 is an explanatory view schematically showing the entire structure of a sealing member.
  • FIG. 3 is an explanatory view showing a portion A shown in FIG. 2 on an enlarged scale.
  • FIG. 4 is an explanatory view showing a cross section taken along line IV—IV in FIG. 3 .
  • FIG. 5 is an explanatory view showing an assembly state of a joint portion of the sealing members.
  • FIG. 6 is an explanatory view showing a partial modification of an essential portion of the sealing structure according to the instant embodiment.
  • FIG. 7 is an explanatory view schematically showing an inter-disk sealing structure for a gas turbine according to another embodiment of the present invention.
  • FIG. 8 is an explanatory view schematically showing a partial modification of the sealing member according to the instant embodiment.
  • FIG. 9 is an explanatory view schematically showing a conventional inter-disk sealing structure in a gas turbine.
  • FIG. 10 is an explanatory view showing a portion X shown in FIG. 9 on an enlarged scale.
  • a first embodiment of the present invention i.e., a first preferred mode for carrying out the invention, will be described with reference to FIG. 1 to FIG. 5 .
  • an annular sealing member formed of a tube which is hollow in cross section is employed in place of the baffle plate 8 used for sealing in the conventional sealing structure, and that another inventive feature can be seen with respect to the position at which the annular sealing member is to be disposed.
  • the sealing structure according to the instant embodiment is substantially similar to the conventional one. Accordingly, illustration in the drawings is restricted to the substantive features of the invention, and parts or components similar to those in the previously described conventional gas turbine are denoted by like reference numerals, and repeated description thereof is omitted.
  • the sealing member 10 is made of a hollow tube shaped in an annular form, as mentioned previously, and is disposed within a groove 7 formed in one of the disk lands 6 which project in opposition to each other between the adjacent disks 1 .
  • the annular sealing member 10 is disposed so that the outer peripheral surface thereof bears on an inner wall surface of the groove 7 and an end face of the opposite disk land 6 .
  • reference numeral 11 denotes bolt holes bored through the individual disks 1 (ordinarily around four disks are juxtaposed), and numeral 12 denotes a bolt which extends through the bolt holes 11 for interconnecting the individual disks 1 in an integral unit.
  • Reference numeral 13 denotes a steam hole which constitutes a passage for supplying the cooling steam.
  • reference numeral 14 denotes curvic couplings formed at tips of protruding portions of the adjacent disks 1 , respectively, and which are meshed so as to prevent the center axes of the disks from deviating.
  • the aforementioned sealing member 10 is formed as an annular body by serially interconnecting four segments, i.e., a segment 10 a , a segment 10 b , a segment 10 c and a segment 10 d , wherein a rotation stopper key 15 is provided in a given one of these segments, as can be seen in FIG. 2 .
  • FIG. 3 showing a portion A shown in FIG. 2 in detail
  • FIG. 4 showing a cross section taken along line IV—IV in FIG. 3
  • FIG. 5 showing an assembly state of the individual parts, in which the joining state of the adjacent segments is illustrated by taking the segment 10 a and the segment 10 d as a representative example
  • an inner sleeve 20 is press-fitted inside each joint portion of the adjacent segments and that an outer sleeve 30 is fitted externally around joined end portions of the segments 10 a and 10 d at a position corresponding to the press-fit position of the inner sleeve 20 , whereby these segments are coupled together.
  • each of the joined end portions of the segment 10 a and the segment 10 d is previously decreased by an amount corresponding to the thickness of the outer sleeve 30 . Accordingly, after the fitting of the outer sleeve 30 , the outer diameter of the joint portion becomes equal to the outer diameter of the sealing member 10 . In this manner, the sealing member 10 is formed as the annular member with a uniform thickness over the entire length.
  • the sealing member 10 can rotate together with the rotation of the rotor portion, whereby a centrifugal force is brought about under which the sealing member 10 is caused to positively bear on the previously mentioned inner wall surface of the groove 7 and the end face of the opposite disk land, whereby sealing can be performed between the adjacent disks 1 . Accordingly, by increasing the weight of the sealing member 10 , sealing surface pressure can be increased, whereby more positive sealing can be realized.
  • the sealing member 10 is constituted by a plurality of segments 10 a to 10 d arrayed circumferentially as an annular body, stress in the circumferential direction due to the centrifugal force can be mitigated, while the sealing member 10 can follow the stretch or elongation of the disk 1 which is caused by heat and centrifugal force. Thus, gaps are not formed at the position of the sealing member. Additionally, the sealing performance of the sealing member is not affected by a difference in the elongation or stretch between the adjacent disks 1 . Thus, the sealing can be reliably performed at the location where the sealing member is disposed.
  • dimensional relationships at the joint portions of the segments 10 a to 10 d joined together may be selected with the values mentioned below.
  • the outer diameter of the inner sleeve 20 and the inner diameter of the segment 10 a , . . . , 10 d press-fitted into the inner sleeve 20 , as represented by ⁇ 1 , is 24 mm
  • the inner diameter of the outer sleeve 30 fitted at the position where the inner sleeve 20 has been inserted and the outer diameter of the segment 10 a , . . . , 10 d located at this position, as represented by ⁇ 2 is 31 mm
  • the outer diameter of the outer sleeve 30 as represented by ⁇ 3 , is 32 mm.
  • the length of the outer sleeve 30 and the inner sleeve 20 is 30 mm
  • the length of the outer sleeve 30 and the inner sleeve 20 over which the outer sleeve and the inner sleeve are fitted into/onto the end portion of the each segment 10 a , . . . , 10 d , as represented by l 2 is 15 mm
  • the thickness of the outer sleeve 30 as represented by t 1
  • the total thickness inclusive of the outer sleeve 30 and the inner sleeve 20 is 3.5 mm.
  • the disk lands 6 which face each other are formed symmetrically with respect to the joining surfaces, i.e., the grooves 7 are formed in both the facing disk lands 6 , 6 , respectively, wherein the sealing member 10 mentioned above may be disposed so that it bears on the inner wall surfaces of the grooves 7 , respectively, as shown in FIG. 6 .
  • annular sealing member having a generally M-shape cross section is employed for sealing instead of the baffle plate 8 used in the conventional seal structure, wherein the annular sealing member is disposed at a particular position which will be described hereinafter.
  • the other parts or portions are substantially the same as the corresponding ones of the conventional structure described hereinbefore. Accordingly, in the following, description of the conventional structure will be referred to, as occasion requires, and repetitive description will be omitted.
  • FIG. 7 only one of a pair of disks 1 disposed adjacent to each other is shown. Consequently, in FIG. 7, a sealing member 110 to be disposed between the paired disks 1 disposed oppositely adjacent to each other is divided into two halves at the center thereof and only one half is shown with the other being omitted from the illustration.
  • an other half portion formed continuously with the member 110 shown at the one side is disposed in association with the other disk positioned in opposition to the aforementioned disk 1 . Accordingly, the figure only shows half of the sealing member 110 which is intrinsically shaped like an M.
  • the sealing member 110 is formed substantially as mentioned above and disposed in a sandwiched manner within grooves 7 which extend in the circumferential direction and which are formed in lower portions of the disk lands 6 protruding in opposition to each other between the adjacent disks 1 .
  • the sealing member 110 formed in the M-like shape is positioned such that each of lower open ends 110 a of the M-like sealing member bears on an oblique inner wall surface of the groove 7 while each of upper ends 110 b of the M-like sealing member is positioned with a small gap relative to a lower surface of the disk land 6 , whereas an intermediate portion 110 c of the M-like sealing member is formed and positioned in a floating state within the space defined between the grooves 7 .
  • the sealing member 110 rotates together with the rotation of the rotor portion, whereby the sealing member is subjected to centrifugal force. Under the influence of the centrifugal force, each of the lower open ends 110 a of the M-like sealing member is forced to bear on the oblique inner wall surface 111 of the aforementioned groove 7 , whereby sealing is performed. Accordingly, by increasing the weight of the sealing member 110 itself, the sealing surface pressure can be increased.
  • the sealing points are defined at locations where each of the lower open ends 110 a of the M-like sealing member 110 bear against the inner oblique wall surface 111 of each of the grooves 7 in which the sealing member 110 is disposed, the sealing performance can be sustained regardless of stretch or elongation of the disk 1 in the radial direction.
  • the sealing member 110 may be integrally formed as viewed in the circumferential direction. However, by forming the sealing member 110 with a plurality of segments divided in the circumferential direction, it is possible to mitigate stress which may be induced in the circumferential direction by centrifugal force.
  • dimensional relationships among the M-like sealing members 110 , the grooves 7 in which the sealing members are disposed and associated peripheral portions may be selected with, for example, values mentioned below.
  • the depth of the groove 7 (distance in the diametrical direction), as represented by l 1 , is 24.5 mm
  • a half of the width (axial distance) of the groove 7 , as represented by l 2 is 28.7 mm
  • the width of the lower open end of the sealing member 110 , as represented by l 3 is 7.5 mm
  • the gap between the upper end 110 b of the sealing member 110 and the lower surface of the disk land 6 , as represented by l 4 is 1.5 mm
  • the thickness of the disk land 6 , as represented by l 5 is 5 mm
  • the angle of inclination of the oblique inner wall surface 111 of the groove 7 on which the lower open end 110 a of the sealing member 110 is forced to bear, as represented by ⁇ is 15°.
  • the sealing member 110 should desirably be made
  • the sealing member 110 is formed in the M-like shape.
  • a sealing member 112 with a generally C-shape such as shown in FIG. 8 may be employed and disposed such that upper and lower curved portions of the C-like sealing member 112 bear against an inner oblique wall surface 111 of the groove 7 .
  • the sealing member need not have exactly the M-like shape but may be formed with a shape similar to an M.
  • the annular sealing member having a hollow cross section is adopted and in which the annular sealing member is disposed in a sandwiched fashion in a groove formed in a circumferential direction in an end face of at least one of disk lands which protrude in opposition to each other from adjacent rotor disks, being brought into contact under pressure with an inner wall surface of the groove and an end face of the other disk land, or alternatively, an inner wall surface of a groove formed in the other disk to thereby realize the inter-disk seal structure for the gas turbine, the inter-disk sealing in the gas turbine can be sustained with high reliability due to the sealing surface pressure which increases under centrifugal force upon rotation of the turbine, whereby the sealing performance can be enhanced, thus contributing greatly to the practical applicability of the steam-jet cooling system.
  • the annular sealing member for realizing the inter-disk sealing in the gas turbine is constituted by continuously coupling a plurality of segments in the annular direction, i.e., in the circumferential direction, the sealing member can follow the stretch or elongation of the rotor disk, which is brought about by heat and the centrifugal force, without being accompanied by stress in the circumferential direction.
  • gaps are not formed at the location of the sealing member.
  • the sealing performance of the sealing member is not affected by differences in the elongation or stretch between adjacent rotor disks.
  • the sealing performance can be reliably maintained, contributing greatly to the practical application of the steam-jet cooling system, as with the arrangement mentioned above.
  • the sealing surface pressure can be increased under centrifugal force upon rotation of the turbine, whereby the sealing performance can be reliably maintained regardless of the stretch or elongation of the rotor disk in the radial direction by appropriately selecting or the contact points between the sealing member and the wall surface. Moreover, the sealing performance can be improved, which can thus make a great contribution to the practical applicability of the steam-jet cooling system.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US09/230,848 1997-06-04 1998-06-03 Seal structure between gas turbine discs Expired - Lifetime US6261063B1 (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
JP9-146475 1997-06-04
JP14647597A JP3310906B2 (ja) 1997-06-04 1997-06-04 ガスタービンディスク間のシール構造
JP9-162647 1997-06-19
JP16264797A JP3342347B2 (ja) 1997-06-19 1997-06-19 ガスタービンディスク間のシール構造
PCT/JP1998/002455 WO1998055736A1 (fr) 1997-06-04 1998-06-03 Structure d'etancheite montee entre les disques d'une turbine a gaz

Publications (1)

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US6261063B1 true US6261063B1 (en) 2001-07-17

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US09/230,848 Expired - Lifetime US6261063B1 (en) 1997-06-04 1998-06-03 Seal structure between gas turbine discs

Country Status (5)

Country Link
US (1) US6261063B1 (fr)
EP (1) EP0921277B1 (fr)
CA (1) CA2262930C (fr)
DE (1) DE69818406T2 (fr)
WO (1) WO1998055736A1 (fr)

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US6733234B2 (en) 2002-09-13 2004-05-11 Siemens Westinghouse Power Corporation Biased wear resistant turbine seal assembly
US6883807B2 (en) 2002-09-13 2005-04-26 Seimens Westinghouse Power Corporation Multidirectional turbine shim seal
US20080166222A1 (en) * 2006-12-15 2008-07-10 Kabushiki Kaisha Toshiba Turbine rotor and steam turbine
US8469656B1 (en) 2008-01-15 2013-06-25 Siemens Energy, Inc. Airfoil seal system for gas turbine engine
US9145786B2 (en) 2012-04-17 2015-09-29 General Electric Company Method and apparatus for turbine clearance flow reduction
US9399926B2 (en) 2013-08-23 2016-07-26 Siemens Energy, Inc. Belly band seal with circumferential spacer
US20170044916A1 (en) * 2015-08-14 2017-02-16 Ansaldo Energia Switzerland AG Gas turbine membrane seal
US20180051715A1 (en) * 2016-08-18 2018-02-22 United Technologies Corporation Method and apparatus for cooling thrust reverser seal
US10077666B2 (en) 2014-09-23 2018-09-18 United Technologies Corporation Method and assembly for reducing secondary heat in a gas turbine engine
US10100642B2 (en) 2015-08-31 2018-10-16 Rolls-Royce Corporation Low diameter turbine rotor clamping arrangement
CN109667627A (zh) * 2017-10-13 2019-04-23 斗山重工业建设有限公司 燃气轮机的转子轮盘总成
EP3078809B1 (fr) 2015-04-10 2019-07-03 United Technologies Corporation Joint labyrinthe rotatif ayant la forme d'un m
US10378453B2 (en) 2014-09-12 2019-08-13 United Technologies Corporation Method and assembly for reducing secondary heat in a gas turbine engine

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JP2006214367A (ja) * 2005-02-04 2006-08-17 Mitsubishi Heavy Ind Ltd 動翼体
US20120263580A1 (en) * 2011-04-14 2012-10-18 General Electric Company Flexible seal for turbine engine
US8956120B2 (en) 2011-09-08 2015-02-17 General Electric Company Non-continuous ring seal
DE102012014109A1 (de) * 2012-07-17 2014-01-23 Rolls-Royce Deutschland Ltd & Co Kg Zwischenscheibendichtung einer Gasturbine
US10385712B2 (en) 2015-05-22 2019-08-20 United Technologies Corporation Support assembly for a gas turbine engine
FR3057300B1 (fr) 2016-10-07 2018-10-05 Safran Aircraft Engines Assemblage d'anneau mobile de turbine de turbomachine

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US6733234B2 (en) 2002-09-13 2004-05-11 Siemens Westinghouse Power Corporation Biased wear resistant turbine seal assembly
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US8469656B1 (en) 2008-01-15 2013-06-25 Siemens Energy, Inc. Airfoil seal system for gas turbine engine
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US9399926B2 (en) 2013-08-23 2016-07-26 Siemens Energy, Inc. Belly band seal with circumferential spacer
US10378453B2 (en) 2014-09-12 2019-08-13 United Technologies Corporation Method and assembly for reducing secondary heat in a gas turbine engine
US10077666B2 (en) 2014-09-23 2018-09-18 United Technologies Corporation Method and assembly for reducing secondary heat in a gas turbine engine
EP3078809B1 (fr) 2015-04-10 2019-07-03 United Technologies Corporation Joint labyrinthe rotatif ayant la forme d'un m
US20170044916A1 (en) * 2015-08-14 2017-02-16 Ansaldo Energia Switzerland AG Gas turbine membrane seal
US10533442B2 (en) * 2015-08-14 2020-01-14 Ansaldo Energia Switzerland AG Gas turbine membrane seal
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US10563671B2 (en) * 2016-08-18 2020-02-18 United Technologies Corporation Method and apparatus for cooling thrust reverser seal
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CN109667627B (zh) * 2017-10-13 2022-01-25 斗山重工业建设有限公司 燃气轮机的转子轮盘总成
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CA2262930A1 (fr) 1998-12-10
EP0921277A1 (fr) 1999-06-09
EP0921277A4 (fr) 2001-01-24
CA2262930C (fr) 2001-10-09
DE69818406D1 (de) 2003-10-30
WO1998055736A1 (fr) 1998-12-10
EP0921277B1 (fr) 2003-09-24
DE69818406T2 (de) 2004-07-01

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